Results
2004-10-07: This amendment supersedes an existing airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 407 helicopters which requires a one-time replacement of certain oil cooler blower bearings. Also, the existing AD requires adding a limitation and caution to the rotorcraft flight manual (RFM) and inspecting, replacing, and lubricating certain bearings at specified intervals. This amendment adds certain segmented drive shaft bearings to the applicability and requires modifying the oil cooler blower inlet ducts and airflow shields and replacing certain bearings. Thereafter, this amendment requires removing the current temporary limitations and inserting revised limitations into the RFM. This amendment also requires revising the inspection and lubrication requirements. This amendment is prompted by several cases of bearing failure. The addition of certain segmented drive shaft bearings is due to two recent failures. The actions specified by this AD are intended toprevent failure of a bearing, loss of tail rotor drive, and a subsequent loss of directional control of the helicopter.
2012-06-19: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes; and Model A340-200 and -300 series airplanes. This AD requires repetitive inspections of the main fitting and sliding tube of the nose landing gear (NLG) for defects, damage, and cracks, and corrective actions if necessary. This AD was prompted by reports of a cracked main fitting and sliding tube during overhaul of NLGs. We are issuing this AD to detect and correct cracks, defects, or damage of the main fitting and sliding tube of the NLG, which could result in failure of the main fitting or sliding tube, and consequent NLG collapse.
2012-06-25: We are superseding an existing airworthiness directive (AD) for Goodrich Evacuation Systems approved under TSO TSO-C69b and installed on Model A330-200 and -300 series airplanes, Model A340-200 and -300 series airplanes, and Model A340-500 and -600 series airplanes. That AD currently requires inspecting to determine the part number of the pressure relief valves on the affected Goodrich evacuation systems, and corrective action if necessary. This new AD requires inspecting to determine the part number of the pressure relief valves on the affected Goodrich evacuation systems and replacing certain pressure relief valves, and adds airplanes to the applicability. This AD was prompted by reports that during workshop testing, certain pressure relief valves, which were required by the existing AD, did not seal and allowed the pressure in certain slides/ rafts to fall below the minimum raft mode pressure for the unit. We are issuing this AD to prevent loss of pressure in the escape slides/rafts after an emergency evacuation, which could result in inadequate buoyancy to support the raft's passenger capacity during ditching and increase the chance for injury to raft passengers.
2021-22-24: The FAA is adopting a new airworthiness directive (AD) for certain MHI RJ Aviation ULC Model CL-600-2C10 (Regional Jet Series 700, 701 & 702), CL-600-2C11 (Regional Jet Series 550), CL-600-2D15 (Regional Jet Series 705), CL-600-2D24 (Regional Jet Series 900), and CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations for structural inspections and safe life components are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
2021-22-23: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 757-200, -200PF, -200CB, and -300 series airplanes. This AD was prompted by crack indications found in the lower aft wing skin bolt holes where the flap tracks attach to the track support fitting; this finding was on a Model 737-300 series airplane, which has a design similar to the Model 757 airplanes. This AD requires repetitive high frequency eddy current (HFEC) inspections for cracking of the lower aft wing skin aft edge at certain flap tracks, and repair if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2004-10-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes equipped with certain Honeywell start converter units (SCU). This amendment requires replacement of the SCU of the auxiliary power unit (APU) located in the electrical and electronics (E/E) compartment with a new or modified SCU. This action is necessary to prevent overheating of the electrical connector of the SCU, which could create an ignition source and possible fire in the E/E compartment and cause damage to certain electrical wire bundles on the E2-2 shelf. Such damage could result in loss of power from the APU generator, failure of electrically powered airplane systems, and consequent reduction in the ability of the flight crew to control the airplane in certain adverse operating conditions. This action is intended to address the identified unsafe condition.
58-26-03: 58-26-03 FAIRCHILD: Applies to all F-27 aircraft. Compliance required as indicated. A number of failures of the Westinghouse P/N 903J826, 903J826-2, 903J826-3 a.c. deicing generators have occurred in service. These generators have been replaced by an improved generator, J/N 903J826-4. Inspect Westinghouse P/N 903J826-4 at the first removal or by 500 hours, whichever comes first, to determine that the bearing support in the mounting bracket is secure with no evidence of looseness or failed rivets. (Fairchild Service Bulletin 24-1 cover this same subject.)
2012-03-01: We are adopting a new airworthiness directive (AD) for Eurocopter Deutschland (ECD) Model EC135 helicopters. This AD results from a mandatory continuing airworthiness information (MCAI) AD issued by the aviation authority of the Federal Republic of Germany, with which we have a bilateral agreement, to identify and correct an unsafe condition. The MCAI AD states that in the past, the FADEC FAIL caution light illuminated on a few EC135 T1 helicopters. It states that this was caused by a discrepancy in the parameters that was generated within the fuel main metering unit and transmitted to the FADEC. This discrepancy led to the display of the FADEC FAIL caution light and ``freezing'' of the fuel main metering valve at its position, resulting in loss of the automatic engine control in the affected system. With the MCAI AD, a synchronization procedure for pilots, which was already used in the past, is being reintroduced, which prevents the parameter discrepancy arising and thus sustains the automatic engine control. The AD actions are intended to prevent failure of the FADEC to automatically meter fuel, indicated by a FADEC FAIL cockpit caution light, and subsequent loss of control of the helicopter.
96-12-03: This amendment adopts a new airworthiness directive (AD) that applies to certain Aviat Aircraft, Inc. (Aviat) Models S-1S, S-1T, S-2, S-2A, S-2S, and S-2B airplanes that are equipped with aft lower fuselage wing attach fittings incorporating either part number (P/N) 76090, 2-2107-1, or 1-210-102. This action requires repetitively inspecting the aft lower fuselage wing attach fitting on both wings for cracks and modifying any cracked aft lower fuselage wing attach fitting. Modifying the aft lower fuselage wing attach fitting on both wings eliminates the repetitive inspection requirement of the AD. Several reports of cracked fuselage wing attach fittings on the affected airplanes prompted this action. The actions specified by this AD are intended to prevent possible in-flight separation of the wing from the airplane caused by a cracked fuselage wing attach fitting.
2004-10-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing transport category airplane models, as listed above. This amendment requires a modification of the air data computer (ADC) system, which involves installing certain new circuit breakers, relays, and related components, and making various wiring changes in and between the flight deck and main equipment center. For certain airplanes, this amendment also requires accomplishment of various other actions prior to or concurrently with the modification of the ADC system. For certain airplanes, this amendment also contains an option that will extend the compliance time to accomplish the modification of the ADC system. This action is necessary to ensure that the flightcrew is able to silence an erroneous overspeed or stall aural warning. A persistent erroneous warning could confuse and distract the flightcrew and lead to an increase in the flightcrew's workload. Such a situation could lead the flightcrew to act on hazardously misleading information, which could result in loss of control of the airplane. This action is intended to address the identified unsafe condition.